轴向压力和端部转矩载荷联合作用下机匣结构稳定性的数值分析  

Structure of aero-engine case under the effect of combined axial pressure and end twist

作　　者：齐红宇[1] 温卫东[2] 孙联文[1] 王林江[2] 

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100083 [2]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《机械设计》2003年第11期25-27,共3页Journal of Machine Design

基　　金：航空发动机结构强度"九五"项目预研资助课题(24.8.1.26)

摘　　要：以某航空发动机复合材料外涵道机匣构件进行结构有限元建模与线性屈曲特性的有限元分析。联接机匣的金属夹层板可起到提高机匣屈曲临界载荷的作用。利用圆柱壳体耦合载荷的研究成果,分析机匣受轴向压力和端部扭矩单独及组合作用下的屈曲行为规律,进而为航空发动机的结构设计提供参考依据,但要求得精确解还需通过实验进行适当的修正。Composite material has already become one of the four main structural materials of aero-engines. The structural finite element modeling and finite element analysis of linear buckling property have been carried out upon an aero-engine case component in composite material of outer culvert of a certain aero-engine. The metallic interrelated board joining the aero-engine case may play a role for enhancing the bulking critical load of the engine case. Utilizing the result of research on coupling load of cylindrical housing, analyzing the law of buckling behavior of the aero-engine case under independent and combined effects of axial pressure and end twist, thus provided basis of reference for the structural design of aero-engines. If an accurate solution is needed it is necessary to advance proper modification through test.

关 键 词：航空发动机 复合材料 机匣 有限元 组合屈曲 稳定性 数值分析 

分 类 号：V214.1[航空宇航科学与技术—航空宇航推进理论与工程] TB115[理学—数学]